Method for modeling spatial shape of fiber composite component of aircraft, involves excluding deviations of spatial shape of sample body by counterpart of tool, and assigning material properties to shell elements of element method model

摘要

The method involves curing a sample body with a layer structure of a fiber composite component on a sample tool. Deviations of spatial shape of the cured sample body are excluded by a counterpart of a sample shaping tool on material properties of the layer structure, where the tool is arranged between two adjacent surfaces at an angle of 30-150 degrees. The material properties are assigned to shell elements of a finite element method (FEM) model. The sample body is provided with standardized dimensions.